Abstract: A composition comprising boron, potassium ferricyanide, and at least one of an oxidizer, a nitramine, a binder, and an additive. Also disclosed are additional compositions, countermeasure devices including the composition, and a method of using the countermeasure device.

Abstract: A rocket propulsion system comprises a combustion chamber, a hydrogen-oxygen supply system connected to the combustion chamber, which hydrogen-oxygen supply system is configured to conduct hydrogen and oxygen into the combustion chamber, and a coolant supply system connected to the combustion chamber, which coolant supply system is configured to conduct a combustible coolant into the combustion chamber. An ignition system of the rocket propulsion system is configured to initiate combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber.

Abstract: Electrically ignitable and electrically controllable explosive material (EIECEM) may be disposed within a shaped charge for deployment downhole. An explosion of the EIECEM is controlled by limiting the duration of excitation at the EIECEM, for example, the duration that an electrical source provides an electrical charge, electrical current or electrical signal. The shaped charge may be insulated from an electrical source to prevent explosion of the EIECEM and coupled to the electrical source to create ignite or explode the EIECEM. A plurality of shaped charges may be disposed downhole and may be ignited or exploded in any suitable order. The EIECEM may be ignited multiple times such that multiple explosions are created. The explosion of the EIECEM creates or extends a perforation or fracture in a formation. The shaped charges may be excited in a predetermined sequence and for a predetermined duration of time.

Abstract: The present invention relates to the field of manufacturing nanoparticles, and specifically to a method for manufacturing diamond nanoparticles, or nanodiamonds, by detonation at least one explosive charge, wherein said at least one explosive charge is nanostructured.

Abstract: The invention is for a startup system for nuclear fusion engines in space. The combustion of hydrogen and oxygen produces heat that is used by a heat engine to produce electricity. This can be supplemented by electricity from other operating engines. The exhaust from the combustion is condensed and electrolyzed to produce hydrogen and oxygen once the engine is in operation. This provides a constant source of energy for future startups. The engine is started up at partial power in electricity generation mode and this power replaces the power from the combustion as it grows. The combustor uses the same heat engine as the nuclear engine uses for power generation.

Abstract: The rate of combustion of an electrically operated propellant having a self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.

Abstract: A very high brisance metal powder explosive is created by including a multitude of hollow aluminum/aluminum oxide micro-particle shells deposited within a high explosive composition matrix. The interior of such micro-particle shells may contain air, nitrogen, other gases, combinations thereof, or possibly even be a vacuum. The invention might be used on warheads that are fragmentation warheads, explosively formed penetrators, air blast warheads, shaped charge jets of shaped charge warheads, or other high explosive-driven devices.

Abstract: A battery housing includes an inner chamber configured to accommodate galvanic cells, in particular lithium-ion cells, which are provided with a cut-out area that can be opened in the event of failure of the cell. In order to prevent, retard and optionally at least partially extinguish a fire in the event of the failure of one or more cells, for example during an accident of an electrically operated vehicle, the inner chamber of the battery housing includes at least one dispenser for dispensing a flame-inhibiting, flame-retarding and/or flame-extinguishing agent. The dispenser has at least one dispenser opening arranged adjacent to a cut-out area of a cell and configured to be opened. The dispenser opening is configured to be opened during a mechanical shock and/or a temperature increase and/or a pressure increase above a predetermined limit value.

Abstract: The present invention relates to a composition comprising bitumen and an alkoxylated amine, to a method for the production of such a composition, and to a method for paving a surface using such a composition. The present invention also relates to an preformulated additive package to be added to bitumen, comprising an alkoxylated amine and an anti-stripping agent.

Abstract: The performance of a mammal, manifested as a reduced oxygen uptake (VO2) during physical exercise, can be enhanced by administering to said mammal a non-toxic amount of nitrate and/or nitrite. Liquid, semi-solid and solid snack and food products and nutritional supplements, such as sport drinks are made available.

Abstract: Reduced toxicity fuels containing hydrocarbons having both strained rings and internal, conjugated triple bonds are disclosed. The fuels described herein are hypergolic with nitrogen tetroxide and/or inhibited red fuming nitric acid.

Abstract: Provided is a fuel of catalytic metal-containing ionic liquid (MCIL) and an IL, to spur hypergolic ignition of such liquids upon contact with an oxidizer to define a hypergolic bipropellant.

Abstract: A group of tertiary amine azides are useful as hypergolic fuels for hypergolic bipropellant mixtures. The fuels provide higher density impulses than monomethyl hydrazine (MMH) but are less toxic and have lower vapor pressures that MMH. In addition, the fuels have shorter ignition delay times than dimethylaminoethylazide (DMAZ) and other potential reduced toxicity replacements for MMH.

Abstract: An energetic ionic liquid catalytic decomposition gas generator uses stoichiometric and nonstoiciometric mixtures of specific energetic ionic liquids and iridium catalyst. The catalyst temperature used and gas production versus ignition may be controlled by combining one or more cationic species with one or more anionic species of the ionic liquid(s).

Abstract: An explosive component includes a first storage container holding a fuel, a second storage container holding an oxidizer, a mixer to mix the fuel and the oxidizer together into an energetic mixture, and a third storage container to hold the energetic mixture.

Abstract: Advanced bipropellant fuels with fast ignition upon mixing with storable oxidizer (N2O4, nitric acid) have been synthesized and demonstrated. The bipropellant fuels are based upon salts containing dicyanamide or tricyanomethanide anions and employ at least two hydrazine functionalities in the cations.

Abstract: Novel monopropellants are provided. The monopropellants are based on N2O, to their preparation method and their uses for space propulsion.

Abstract: Hypergolic liquid or gel fuel mixtures utilized in bipropellant propulsion systems are disclosed as replacements for fuels containing toxic monomethylhydrazine. The fuel mixtures include one or more amine azides mixed with one or more tertiary diamine, tri-amine or tetra-amine compounds. The fuel mixtures include N,N,N?,N?-tetramethylethylenediamine (TMEDA) mixed with 2-N,N-dimethylaminoethylazide (DMAZ), TMEDA mixed with tris(2-azidoethyl)amine (TAEA), and TMEDA mixed with one or more cyclic amine azides. Each hypergolic fuel mixture provides a reduced ignition delay for combining with an oxidant in fuel propellant systems. The fuel mixtures have advantages in reduced ignition delay times compared to ignition delay times for each unmixed component, providing a synergistic effect which was not predictable from review of each component's composition.

Abstract: A method for preparing a gelled liquid propane (GLP) composition comprises the introduction of liquid propane into an evacuated mixing vessel containing a gellant and mixing the liquid propane with the gellant. A bi-propellant system comprising GLP is particularly well-suited for outer planet missions greater than 3 AU from the sun and also functions in earth and near earth environments. Additives such as powders of boron, carbon, lithium, and/or aluminum can be added improve performance or enhance hypergolicity. The gelling agent can be silicon dioxide, clay, carbon, or organic or inorganic polymers. The bi-propellant system may be, but need not be, hypergolic.

Abstract: An ionic liquid is disclosed. A precursor composition that comprises at least one ionic liquid and at least one energetic material is also disclosed, as is a method of synthesizing an ionic liquid and a method of desensitizing an explosive composition.

Abstract: A group of tertiary amine azides are useful as hypergolic fuels for hypergolic bipropellant mixtures. The fuels provide higher density impulses than monomethyl hydrazine (MMH) but are less toxic and have lower vapor pressures that MMH. In addition, the fuels have shorter ignition delay times than dimethylaminoethylazide (DMAZ) and other potential reduced toxicity replacements for MMH.

Abstract: Method and device for mixing and initiating a pyrotechnic charge, comprising at least one coherent porous fuel structure (16) and at least one oxidizer (8). According to the invention, the coherent porous fuel structure (16) and the oxidizer (8) are placed apart in a mixing device (1, 20) to prevent unintentional ignition, and in which the oxidizer (8), in response to the action of a force upon the mixing device (1, 20), for example upon firing of an artillery shell, is transported into the coherent porous fuel structure (16), after which the obtained pyrotechnic charge is initiated after a set time delay.

Abstract: A process for making metal-organic frameworks and metal-organic frameworks having host-guest complexes of either liquid energetics, solid energetics, or solid oxidizers.

Abstract: The invention relates to a fuel component for an explosive, in which case the fuel component contains a volume-expanded molecularly dispersed hydrocarbon, and a method for its production. Furthermore, the invention relates to an explosive formed of the fuel component and an oxidizer, an explosive body filled with the explosive as well as an explosion method.

Abstract: A rocket propulsion oxidizer compound that is a mixture that is a homogenous and stable liquid at room temperature that includes nitrous oxide and nitrogen tetroxide.

Abstract: An explosive emulsion to be used in conjunction with a gas-producing agent, such as sodium nitrite, to form an explosive emulsion with a density between 0.50 g/cm3 and 0.90 g/cm3. The present invention also includes the method for producing the explosive emulsion. The explosive emulsion is stable for at least 96 hours with nitrogen bubbles, having a predetermined dimension range, homogenously distributed. To maintain this low-density explosive emulsion stable, between 84% and 95% by weight of an oxidizing solution is combined with 5% to 16% by weight of a fuel solution. The fuel solution includes solid cacao fat as a stabilizing agent and stearic acid to prevent the combination of the nitrogen bubbles. The method for producing the oxidizing solution includes combining ammonium nitrate, sodium nitrate, thiourea, urea, and water at a temperature between 80 and 90 degrees centigrade. In another step of the method, a fuel solution is produced by combining an emulsifier, oil, diesel No.

Abstract: This invention relates to explosive grade ammonium nitrate porous granules. The granules are produced in a fluidized bed and are formed through a combination of layering and agglomeration to produce ammonium nitrate granules are spherical in shape, smooth, hard and dry and do not break down easily during handling. Ammonium nitrate granules of a specific size range and density can be prepared and the size range and density of the granules can be varied, depending on the application of the granules, and this has particular advantages in preparing granules for use in ANFO explosive compositions.

Abstract: The invention relates to a method for producing (cryogenic) solid monopropellants which are cooled to below room temperature and are used for rocket drives, especially using heterogeneous liquid-solid propellants wherein at least one of the reactants in the form of an oxidizer or a fuel contains a phase which is liquid or gaseous at normal temperature, for example emulsions of liquid constituents which do not dissolve in each other, suspensions of solid in liquid constituents or liquid-impregnated feed materials. The invention also relates to a cryogenic solid propellant for rocket drives, especially heterogeneous quasi-monopropellant fuel-oxidizer combinations.

Abstract: A method for preparing a gelled liquid propane (GLP) composition comprises the introduction of liquid propane into an evacuated mixing vessel containing a gellant and mixing the liquid propane with the gellant. A bi-propellant system comprising GLP is particularly well-suited for outer planet missions greater than 3 AU from the sun and also functions in earth and near earth environments. Additives such as powders of boron, carbon, lithium, and/or aluminum can be added improve performance or enhance hypergolicity. The gelling agent can be silicon dioxide, clay, carbon, or organic or inorganic polymers. The bi-propellant system may be, but need not be, hypergolic.

Abstract: The present invention provides a liquid gas generating composition comprising the following (a) to (c) components, wherein the content ratio of (b) component is 0.5 mass % or more and less than 5.0 mass %: (a) hydroxyammonium nitrate; (b) a thickening stabilizer; and (c) water.

Abstract: A method for gassing an emulsion explosives to sensitize the explosive to detonation and/or for density modification is described. The method comprises reacting a compound having an enol group, or a deprotonated enolate form of the enol group, with a nitrosating agent to generate nitric oxide to gas the explosive. The compound reacted with the nitrosating agent can be a lactone such as ascorbic acid. Dinitrogen trioxide is particularly useful as the nitrosating agent.

Abstract: A cost-effective, renewable ethanol-based solid fuel compound, and method of making the fuel for hybrid rocket engines. Gelling agents, preferably methylcellulose can be used in conjunction with calcium acetate or calcium acetate alone make a stiff plastic out of ethanol to improve its properties for hybrid rocket engine. The increased stiffness of an ethanol-based fuel gel, increases yield stress that allows rapid acceleration of rockets. The low cost bio-fuel based on solidified ethanol rather than expensive petroleum derived substances lowers the cost of volume rocket launches, lowers the cost of access to orbit and provides safer sounding rocket flights into space. The resulting raw gel can further be mixed with a cross linking compound and water to form a stiffer material. Alternatively, the resulting raw gel can be frozen by liquid nitrogen.

Abstract: Oligoesters including residues of alk(en)yl succinic anhydrides and polyols having at least 3 OH groups, optionally further esterified with fatty acid residues are surfactants which can be used for emulsifiers or similar uses. The surfactants are usually made from C8 to C30 alk(en)yl succinic anhydride and polyols having at least 4 hydroxyl groups and are particularly of the formula (I): R1—[OR2O(O)C.C(HR3).(HR4)C.C(O)]m—R5 (I), where R1, R2, R3, R4, R5, R6, R7 and m have defined meanings. The surfactants are useful as emulsifiers, particularly oil in water emulsifiers.

Abstract: Hypergolic liquid or gel fuel mixtures utilized in bipropellant propulsion systems are disclosed as replacements for fuels containing toxic monomethylhydrazine. The fuel mixtures include one or more amine azides mixed with one or more tertiary diamine, tri-amine or tetra-amine compounds. The fuel mixtures include N,N,N?,N?-tetramethylethylenediamine (TMEDA) mixed with 2-N,N-dimethylaminoethylazide (DMAZ), TMEDA mixed with tris(2-azidoethyl)amine (TAEA), and TMEDA mixed with one or more cyclic amine azides. Each hypergolic fuel mixture provides a reduced ignition delay for combining with an oxidant in fuel propellant systems. The fuel mixtures have advantages in reduced ignition delay times compared to ignition delay times for each unmixed component, providing a synergistic effect which was not predictable from review of each component's composition.

Abstract: A method for manufacture and delivery of an emulsion explosive having a discontinuous oxidizer solution phase, a continuous fuel phase, and an emulsifier, the method comprising: (a) providing an emulsion manufacturing system; (b) conveying an oxidizer solution phase to the emulsion manufacturing system at a pre-determined pressure; (c) conveying a fuel phase to the emulsion manufacturing system at a pre-determined pressure; (d) forming an emulsion from the oxidizer solution and the fuel phases using only a portion of the pre-determined pressures so as to provide a usable residual pressure after the formation of the emulsion; and (e) utilizing the residual pressure to non-mechanically deliver the emulsion to a pre-determined location.

Abstract: Provided is a hypergolic bipropellant formed by combining a IL fuel having a dicyanamide anion and a nitrogen-containing, heterocyclic-based cation with an oxidizer for such fuel.

Abstract: An ionic liquid is disclosed A precursor composition that comprises at least one ionic liquid and at least one energetic material is also disclosed, as is a method of synthesizing an ionic liquid and a method of desensitizing an explosive composition.

Abstract: An explosive device and methods for forming same, the device comprising a portion of nitrous oxide and a portion of fuel. In one example, the explosive device may include a first storage area containing said portion of nitrous oxide, and a second storage area containing said portion of fuel, wherein the first storage area selectively maintains the portion of nitrous oxide separated from the fuel in the second storage area prior to detonation of the explosive device. In another example, in the event the explosive fails to detonate, the explosive device may include a vent valve for discharging the nitrous oxide from the explosive device to reduce or eliminate its explosive characteristics. The explosive device can be used for various applications, including but not limited to military weapons, pyrotechnic devices, or civil blasting explosives, for example.

Abstract: Ammonium dinitramide based liquid monopropellants exhibiting stabilised combustion characteristics and improved storage life, containing ammonia, a base weaker than ammonia, or a base which is sterically hindered, added in an amount of 0.1 to 5% of the total weight of the other components of the propellant.

Abstract: An explosive device and methods for forming same, the device comprising a portion of nitrous oxide and a portion of fuel. In one example, the explosive device may include a first storage area containing said portion of nitrous oxide, and a second storage area containing said portion of fuel, wherein the first storage area selectively maintains the portion of nitrous oxide separated from the fuel in the second storage area prior to detonation of the explosive device. In another example, in the event the explosive fails to detonate, the explosive device may include a vent valve for discharging the nitrous oxide from the explosive device to reduce or eliminate its explosive characteristics. The explosive device can be used for various applications, including but not limited to military weapons, pyrotechnic devices, or civil blasting explosives, for example.

Abstract: The present invention is a bi-propellant system comprising a gelled liquid propane (GLP) fuel and a gelled MON-30 (70% N2O4+30% NO) oxidizer. The bi-propellant system is particularly well-suited for outer planet missions greater than 3 AU from the sun and also functions in earth and near earth environments. Additives such as powders of boron, carbon, lithium, and/or aluminum can be added to the fuel component to improve performance or enhance hypergolicity. The gelling agent can be silicon dioxide, clay, carbon, or organic or inorganic polymers. The bi-propellant system may be, but need not be, hypergolic.

Abstract: Oligoesters including residues of alk(en)yl succinic anhydrides and polyols having at least 3 OH groups, optionally further esterified with fatty acid residues are surfactants which can be used for emulsifiers or similar uses. The surfactants are usually made from C8 to C30 alk(en)yl succinic anhydride and polyols having at least 4 hydroxyl groups and are particularly of the formula (I): R1—[OR2O(O)C.C(HR3).(HR4)C.C(O)]m—R5 (I), where R1, R2, R3, R4, R5, R6, R7 and m have defined meanings. The surfactants are useful as emulsifiers, particuarly oil in water emulsifiers.

Abstract: A method and apparatus for gelling liquid propane and other liquefied gasses includes a temperature controlled churn mixer, vacuum pump, liquefied gas transfer tank, and means for measuring amount of material entering the mixer. The apparatus and method are particularly useful for the production of high quality rocket fuels and propellants.

Abstract: An explosive device and methods for forming same, the device comprising a portion of nitrous oxide and a portion of fuel. In one example, the explosive device may include a first storage area containing said portion of nitrous oxide, and a second storage area containing said portion of fuel, wherein the first storage area selectively maintains the portion of nitrous oxide separated from the fuel in the second storage area prior to detonation of the explosive device. In another example, in the event the explosive fails to detonate, the explosive device may include a vent valve for discharging the nitrous oxide from the explosive device to reduce or eliminate its explosive characteristics. The explosive device can be used for various applications, including but not limited to military weapons, pyrotechnic devices, or civil blasting explosives, for example.

Abstract: A thermobaric explosive composition is provided that includes coated fuel particle, a nitramine, and binder. The coated fuel particles preferably have a magnesium core and an aluminum coating. Upon detonation, the nitramine disperses the coated fuel particles over a blast area during a first overpressure stage. The aluminum coating of the fuel particles has a thickness selected to provide an amount of aluminum that is stoichiometrically less than an amount of ambient-air oxygen available in the blast area for aerobic combustion with the aluminum during the first overpressure stage. Once exposed, the magnesium cores may combust to increase the impulse generated in the first overpressure stage. Also provided are articles of manufacture and related methods.

Abstract: A method for supplying a pyrotechnic material slurry to a container, includes, taking out a pyrotechnic material slurry, stored inside a storage container, from the bottom portion of the storage container or a vicinity thereof, sealing the exposed surface of the pyrotechnic material slurry with a sealing material, and maintaining the sealed state of the pyrotechnic material slurry in the process of supplying the pyrotechnic material slurry to the container.

Abstract: Explosives containing aqueous oxidizer solution, fuel, and a nanoparticle-stabilized foam sensitizer. The explosives may also further contain an emulsifier.

Abstract: Provided are energetic materials of low vapor pressure in the form of ionic liquids having fuel and oxidizer ions including, substituted pyridinium or imidazolium cations paired with nitrato-, perchlorato-, or nitramido-based anions, to form such ionic liquids or salts. The salts of the present invention are low melting and have essentially little or no vapor pressure over a wide temperature range. The salts of this invention are thus an important breakthrough since they can serve as high-performing monopropellants which are not complex mixtures and have no vapor toxicity. Such salts also find use as munitions, liquid explosives, reaction media for the synthesis of other high-energy materials, and as plasticizers.

Abstract: A method of transporting a liquid product down a vertical conduit having an inlet provided at the top of the conduit and an outlet provided at the bottom of the conduit, which method comprises feeding the liquid product into the inlet of the conduit and contacting the liquid product with means for dissipating potential energy released by the liquid product as it is transported down the conduit so that turbulence in the liquid product at the outlet of the conduit is reduced.

Abstract: Disclosed is a group of tertiary amine azides useful as hypergolic fuels for hypergolic bipropellant mixtures. The fuels provide higher density impulses than monomethyl hydrazine (MMH) but are less toxic and have lower vapor pressures that MMH. In addition, the fuels have shorter ignition delay times than dimethylaminoethylazide (DMAZ) and other potential reduced toxicity replacements for MMH.